Federal Register / Vol. 79, No. 191 / Thursday, October 2, 2014 / Proposed Rules 59463 

No. AE 3007A–A–72–407, Revision 1, dated 

August 29, 2014, except those S/Ns excluded 

by Table 1, Table 2, Table 4, and Table 5 of 

RRC ASB No. AE 3007A–A–72–407, Revision 

1, dated August 29, 2014. 

(3) With an installed HPT stage 2 wheel, 

P/N 23084520 or 23088818, all S/Ns listed in 

Table 1 and Table 2 of RRC ASB No. AE 

3007C–A–72–316, dated December 6, 2013, 

except those S/Ns excluded by Table 1 of 

RRC ASB No. AE 3007C–A–72–316, dated 

December 6, 2013. 

(4) With an installed 4th stage turbine 

wheel, P/N 23083536, all S/Ns listed in Table 

2 of RRC ASB No. AE 2100P–A–72–019, 

dated July 25, 2013. 

(d) Unsafe Condition 

This AD was prompted by reports of 

pitting in the wheel bores and subsequent 

RRC analysis that concluded that lower life 

limits are needed for the affected turbine 

wheels. We are issuing this AD to prevent 

uncontained failure of the turbine wheels, 

damage to the engine, and damage to the 

airplane. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) For all RRC AE 3007A1, A1/1, A1/3, 

A1E, A1P, and A3 series engines with an 

HPT stage 2 wheel P/N and S/N identified in 

RRC ASB No. AE 3007A–A–72–408, Revision 

1, dated August 29, 2014, at each shop visit 

after the effective date of this AD, eddy 

current inspect the bore of the affected HPT 

stage 2 wheels. Use RRC ASB AE 3007A–A– 

72–408, Revision 1, August 29, 2014, to do 

the inspection. Do not return to service any 

wheel that fails the inspection required by 

this AD. 

(2) Thirty days after the effective date of 

this AD, do not return to service any engine 

that has a turbine wheel with a P/N and an 

S/N listed in any of the following RR ASBs 

whose wheel life exceeds the new life limits 

identified in the RR ASBs: 

RRC ASB No. AE 2100D2–A–72–085, dated 

July 25, 2013; 

RRC ASB No. AE 2100D3–A–72–277, dated 

July 25, 2013; 

RRC ASB No. AE 2100P–A–72–019, dated 

July 25, 2013; 

RRC ASB No. AE 3007A–A–72–407, 

Revision 1, dated August 29, 2014; or 

RRC ASB No. AE 3007C–A–72–316, dated 

December 6, 2013. 

(f) Installation Prohibition 

Thirty days after the effective date of this 

AD, do not install an affected wheel, as 

identified in paragraph (c) of this AD, into 

any RRC AE 3007C2 engine. 

(g) Definition 

For the purpose of this AD, an ‘‘engine 

shop visit’’ is the induction of an engine into 

the shop for maintenance involving the 

separation of pairs of major mating engine 

flanges, except that the separation of engine 

flanges solely for the purposes of 

transportation without subsequent engine 

maintenance is not an engine shop visit. 

(h) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Chicago Aircraft 

Certification Office, FAA, may approve 

AMOCs for this AD. Use the procedures 

found in 14 CFR 39.19 to make your request. 

(i) Related Information 

(1) For more information about this AD, 

contact Kyri Zaroyiannis, Aerospace 

Engineer, Chicago Aircraft Certification 

Office, Small Airplane Directorate, FAA, 

2300 E. Devon Ave., Des Plaines, IL 60018; 

phone: 847–294–7836; fax: 847–294–7834; 

email: kyri.zaroyiannis@faa.gov. 

(2) RRC ASB No. AE 2100D2–A–72–085, 

dated July 25, 2013; RRC ASB No. AE 

2100D3–A–72–277, dated July 25, 2013; RRC 

ASB No. AE 2100P–A–72–019, dated July 25, 

2013; RRC ASB No. AE 3007A–A–72–407, 

Revision 1, dated August 29, 2014; RRC ASB 

No. AE 3007A–A–72–408, Revision 1, dated 

August 29, 2014; and RRC ASB No. AE 

3007C–A–72–316, dated December 6, 2013, 

which are not incorporated by reference in 

this AD, can be obtained from RRC using the 

contact information in paragraph (i)(3) of this 

AD. 

(3) For service information identified in 

this AD, contact Rolls-Royce Corporation, 

450 South Meridian Street, Mail Code NB– 

01–06, Indianapolis, IN 46225, phone: 317– 

230–1667; email: CMSEindyOSD@rollsroyce.com; Internet: www.rolls-royce.com. 

(4) You may view this service information 

at the FAA, Engine & Propeller Directorate, 

12 New England Executive Park, Burlington, 

MA. For information on the availability of 

this material at the FAA, call 781–238–7125. 

Issued in Burlington, Massachusetts, on 

September 25, 2014. 

Colleen M. D’Alessandro, 

Assistant Directorate Manager, Engine & 

Propeller Directorate, Aircraft Certification 

Service. 

[FR Doc. 2014–23561 Filed 10–1–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0961; Directorate 

Identifier 2011–NE–22–AD] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

Corporation Turboprop and Turboshaft 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

airworthiness directive (AD) 2012–14– 

06, which applies to certain Rolls-Royce 

Corporation (RRC) 250–C20, –C20B, and 

–C20R/2 turboshaft engines. AD 2012– 

14–06 currently requires a one-time 

visual inspection and fluorescentpenetrant inspection (FPI) on certain 

3rd-stage and 4th-stage turbine wheels 

for cracks in the turbine blades. Since 

we issued AD 2012–14–06, we 

determined that the one-time inspection 

required by AD 2012–14–06 should be 

changed to repetitive inspections and 

that we should add an inspection after 

any engine hot start. We also identified 

additional engine models subject to the 

unsafe condition. This proposed AD 

would replace the one-time visual 

inspection and FPI with repetitive 

visual inspections and FPIs, and would 

also require inspection and FPI after any 

engine hot start. This proposed AD 

would also add certain engine models to 

the applicability. We are proposing this 

AD to prevent failure of 3rd-stage and 

4th-stage turbine wheel blades, which 

could cause engine failure and damage 

to the aircraft. 

DATES: We must receive comments on 

this proposed AD by December 1, 2014. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Rolls-Royce 

Corporation, 450 South Meridian Street, 

Indianapolis, IN 46225–1103; phone: 

888–255–4766 or 317–230–2720; email: 

helicoptercustsupp@rolls-royce.com; 

Internet: www.rolls-royce.com. You may 

view this service information at the 

FAA, Engine & Propeller Directorate, 12 

New England Executive Park, 

Burlington, MA. For information on the 

availability of this material at the FAA, 

call 781–238–7125. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2011– 

0961; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed AD, the 

regulatory evaluation, any comments 


rmajette on DSK2VPTVN1PROD with RULES
59464 Federal Register / Vol. 79, No. 191 / Thursday, October 2, 2014 / Proposed Rules 

received, and other information. The 

street address for the Docket Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: John 

Tallarovic, Aerospace Engineer, Chicago 

Aircraft Certification Office, FAA, 2300 

E. Devon Ave., Des Plaines, IL 60018; 

phone: 847–294–8180; fax: 847–294– 

7834; email: john.m.tallarovic@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2011–0961; Directorate Identifier 

2011–NE–22–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD because of those 

comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

On June 25, 2012, we issued AD 

2012–14–06, Amendment 39–17120 (77 

FR 40479, July 10, 2012), for certain 

RRC 250–C20, –C20B, and –C20R/2 

turboshaft engines with 3rd-stage 

turbine wheel, part number (P/N) 

23065818, and 4th-stage turbine wheel, 

P/N 23055944, installed. AD 2012–14– 

06 requires a one-time visual inspection 

and FPI on certain 3rd-stage and 4thstage turbine wheels for cracks in the 

turbine blades. AD 2012–14–06 resulted 

from seven cases of released turbine 

blades and shrouds, which led to loss of 

power and engine in-flight shutdowns. 

We issued AD 2012–14–06 to prevent 

failure of 3rd-stage and 4th-stage turbine 

wheel blades, which could cause engine 

failure and damage to the aircraft. 

Actions Since AD 2012–14–06 Was 

Issued 

Since we issued AD 2012–14–06, 

Amendment 39–17120 (77 FR 40479, 

July 10, 2012), investigations of 3rdstage and 4th-stage turbine wheel blade 

failures found that the one-time 

inspection required by that AD was not 

identifying all failures. We determined 

that repetitive inspections, triggered by 

hours since last inspection (HSLI) or 

any hot start event, are required to 

address the unsafe condition. We also 

identified additional engine models that 

are subject to the unsafe condition, and 

have added those engine models to the 

applicability of this AD. 

Relevant Service Information 

We reviewed RRC Alert Commercial 

Engine Bulletin (CEB) No. CEB–A–1407, 

Revision 3, dated May 19, 2014, and 

CEB No. CEB–A–72–4098, Revision 3, 

dated May 19, 2014 (combined into one 

document). The service information 

describes procedures for inspecting the 

3rd-stage and 4th-stage turbine wheels. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

Proposed AD Requirements 

This proposed AD would retain the 

initial inspection requirements of AD 

2012–14–06, Amendment 39–17120 (77 

FR 40479, July 10, 2012). This proposed 

AD would require repetitive visual 

inspections and FPIs of the 3rd-stage 

and 4th-stage turbine wheels based on 

HSLI. This proposed AD would also 

require visual inspection and FPI of the 

3rd-stage and 4th-stage turbine wheels 

whenever an engine hot start occurs. We 

have added the requirement for 

opportunity inspections when the 

turbine is already disassembled because 

of the repetitive nature of this 

inspection. This proposed AD would 

also expand the applicability of this AD 

to include additional engine models. 

Costs of Compliance 

We estimate that this proposed AD 

affects 3,769 engines installed on 

aircraft of U.S. registry. We also estimate 

that it would take about 1 hour per 

engine to comply with the recurring 

inspection requirement of this AD. We 

estimate that about 19 engines will 

require an inspection following a hot 

start, and that it would take about 27 

hours per engine to perform that 

inspection. The average labor rate is $85 

per hour. Based on these figures, we 

estimate the cost of this proposed AD on 

U.S. operators to be $363,970. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

Section 106, describes the authority of 

the FAA Administrator. Subtitle VII, 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701, 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We have determined that this 

proposed AD would not have federalism 

implications under Executive Order 

13132. This proposed AD would not 

have a substantial direct effect on the 

States, on the relationship between the 

national Government and the States, or 

on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that the proposed regulation: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

the DOT Regulatory Policies and 

Procedures (44 FR 11034, February 26, 

1979), 

(3) Will not affect intrastate aviation 

in Alaska to the extent that it justifies 

making a regulatory distinction, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. Amend § 39.13 by removing 

airworthiness directive (AD) 2012–14– 

06, Amendment 39–17120 (77 FR 

40479, July 10, 2012), and adding the 

following new AD: 


rmajette on DSK2VPTVN1PROD with RULES
Federal Register / Vol. 79, No. 191 / Thursday, October 2, 2014 / Proposed Rules 59465 

Rolls-Royce Corporation (Type Certificate 

Previously Held by Allison Engine 

Company and Allison Gas Turbine 

Division of General Motors): Docket No. 

FAA–2011–0961; Directorate Identifier 

2011–NE–22–AD. 

(a) Comments Due Date 

The FAA must receive comments on this 

AD action by December 1, 2014. 

(b) Affected ADs 

This AD supersedes AD 2012–14–06, 

Amendment 39–17120 (77 FR 40479, July 10, 

2012). 

(c) Applicability 

This AD applies to Rolls-Royce 

Corporation (RRC) 250–B17, –B17B, –B17C, 

–B17D, –B17E, –B17F, –B17F/1, –B17F/2 

turboprop engines; and RRC 250–C20, 

–C20B, –C20F, –C20J, –C20R, –C20R/1,– 

C20R/2, –C20R/4, –C20S and –C20W 

turboshaft engines with 3rd-stage turbine 

wheel, part number (P/N) 23065818, and 4thstage turbine wheel, P/N 23055944, installed. 

(d) Unsafe Condition 

This AD was prompted by investigations 

that revealed that not all 3rd-stage and 4thstage turbine wheel blade failures were 

identified by the one-time inspections 

required by AD 2012–14–06, Amendment 

39–17120 (77 FR 40479, July 10, 2012). We 

determined that to address the unsafe 

condition, repetitive inspections are 

required, triggered by hours since last 

inspection (HSLI) or any hot start event. We 

are issuing this AD to prevent failure of 3rdstage and 4th-stage turbine wheel blades, 

which could cause engine failure and damage 

to the aircraft. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. After the effective date of this AD: 

(1) Within 1,750 HSLI, remove the affected 

turbine wheels and perform a visual 

inspection and a fluorescent-penetrant 

inspection (FPI) on the removed turbine 

wheels for cracks at the trailing edge of the 

turbine blades near the fillet at the rim. 

(2) Any time there is a hot start, 

immediately perform a visual inspection and 

an FPI on the affected turbine wheels for 

cracks at the trailing edge of the turbine 

blades, near the fillet at the rim. 

(3) Any time the power turbine is 

disassembled, perform a visual inspection 

and an FPI on the affected turbine wheels for 

cracks at the trailing edge of the turbine 

blades, near the fillet at the rim. 

(4) Thereafter, re-inspect every 1,750 HSLI. 

(5) Do not return to service any turbine 

wheels that have cracks detected. 

(f) Definition 

For the purpose of this AD, an engine hot 

start is any time the turbine temperature 

exceeds 1,490 °F for 10 seconds or more, or 

exceeds 1,700 °F for any duration. 

(g) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Chicago Aircraft 

Certification Office, may approve AMOCs for 

this AD. Use the procedures found in 14 CFR 

39.19 to make your request. 

(h) Related Information 

(1) For more information about this AD, 

contact John Tallarovic, Aerospace Engineer, 

Chicago Aircraft Certification Office, FAA, 

2300 E. Devon Ave., Des Plaines, IL 60018; 

phone: 847–294–8180; fax: 847–294–7834; 

email: john.m.tallarovic@faa.gov. 

(2) RRC Alert Commercial Engine Bulletin 

(CEB) No. CEB–A–1407, Revision 3, dated 

May 19, 2014, and CEB No. CEB–A–72–4098, 

Revision 3, dated May 19, 2014 (combined 

into one document), which are not 

incorporated by reference in this AD, can be 

obtained from RRC, using the contact 

information in paragraph (h)(3) of this AD. 

(3) For service information identified in 

this AD, contact Rolls-Royce Corporation 

Customer Support, 450 South Meridian 

Street, Indianapolis, IN 46225–1103; phone: 

888–255–4766 or 317–230–2720; email: 

helicoptercustsupp@rolls-royce.com; 

Internet: www.rolls-royce.com. 

(4) You may view this service information 

at the FAA, Engine & Propeller Directorate, 

12 New England Executive Park, Burlington, 

MA 01803. For information on the 

availability of this material at the FAA, call 

781–238–7125. 

Issued in Burlington, Massachusetts, on 

September 23, 2014. 

Colleen M. D’Alessandro, 

Assistant Directorate Manager, Engine & 

Propeller Directorate, Aircraft Certification 

Service. 

[FR Doc. 2014–23553 Filed 10–1–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0759; Directorate 

Identifier 2014–CE–028–AD] 

RIN 2120–AA64 

Airworthiness Directives; Alpha 

Aviation Concept Limited Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Alpha Aviation Concept Limited Model 

R2160 airplanes. This proposed AD 

results from mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as paint adherence defects 

inside the engine air intake box and 

cohesion defects inside the laminated 

ducting from the filter to the air intake 

box. We are issuing this proposed AD to 

require actions to address the unsafe 

condition on these products. 

DATES: We must receive comments on 

this proposed AD by November 17, 

2014. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE, 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

For service information identified in 

this proposed AD, contact Alpha 

Aviation, 59 Hautapu Road, RD 1, 

Cambridge 3493, New Zealand; 

telephone: +64 7 827 0528; fax: +64 7 

929 2878; Internet: 

www.alphaaviation.co.nz. You may 

review this referenced service 

information at the FAA, Small Airplane 

Directorate, 901 Locust, Kansas City, 

Missouri 64106. For information on the 

availability of this material at the FAA, 

call (816) 329–4148. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0759; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(telephone (800) 647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: Karl 

Schletzbaum, Aerospace Engineer, FAA, 

Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

phone: (816) 329–4123; fax: (816) 329– 

4090; email: karl.schletzbaum@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 


rmajette on DSK2VPTVN1PROD with RULES